Rocket launcher



Dec. 24, 1957 D. F. GUNDER ROCKET LAUNCHER 4 SheetsSheet 1 Filed May 10. 1951 Zlvwwvtom l'lwiglfl- E Eiunder D. F. GUNDER ROCKET LAUNCHER Dec. 24, 1957 4 Sheets-Sheet 2 Filed ma 10, 1951 35 WmmW emm Dec. 24, 1957 D. F. GUNDER 7,

ROCKET LAUNCHER Filed May 10, 1951 4 Sheets-Sheet 5 gwvwwtom Ilwial-fi E [Sunder may:

. Dec. 24, 1957 D. F. GUNDER ROCKET LAUNCHER 4 Sheets-Sheet 4 Fi led May 10. 1951 lll' I'llllll Dwi 5111: F. Sunder 2,817,272 ROCKET LAUNCHER Dwight F. Gander, Ithaca, N. Y., assignor to the United States of America as represented by the Secretary of the Army Application May 10, 1951, Serial No. 225,657

6 Claims. (Cl. 891.7)

(Granted under Title 35, U. S. Code (1952), see. 266) The invention described in the specification and claims may be manufactured and used by or for the Government for governmental purposes without the payment of any royalty thereon.

This invention relates to rocket launchers particularly for use upon tanks and other confined enclosures where a discharge of propellent gases rearwardly into an occupied enclosed space is not permissible.

It is the principal object of the invention to provide a rocket launcher which is easily and quickly loaded, positive and safe in operation both as regards enemy fire and improper operation or loading.

Another object is to provide a launcher having an easily operated breechblock which, when closed, efiectively seals the launcher tube against the rearward discharge of propellent gases and directs such gas-es forwardly out of the muzzle portion of the tube.

Still another object is to provide a rocket launcher which is readily adaptable to a conventional gun mount and its elevating and aiming means.

A further object is to provide a launcher tube which is relatively simple to construct, easy to aim and which positively guides the rocket in a desired initial trajectory during launching.

Yet another object is to provide latch mechanism which cooperates with a rocket to releasably secure the same in proper firing position longitudinally within the tube and .at the same time, enables the rocket to travel forwardly .after initiation.

Gther objects and advantages will be apparent after a study of the following detailed description in connection with the drawings.

In the drawings:

Figure 1 is a side elevation of the launcher mounted in Q the turret at zero or point blank elevation, the turret and shield being shown in section.

Figure 2 is a longitudinal vertical axial section to an enlarged scale through the breech portion of the launcher and showing the breechblock in closed position and a rocket ready for launching.

Figure 3 is a longitudinal horizontal section to a scale reduced from Figure 2, and taken in offset planes identified by the line 33 of Figure 2.

Figure 4 is a rear elevation of the launcher to the same scale as Figure 3, the brcechblock being shown closed and rack and pinion covers removed.

Figure 5 is a transverse section through the launcher tube in a plane identified by the line 55 of Figure 2.

Figure 6 is a transverse section taken in a plane identified by the line 6-6 of Figure 3.

Figure 7 is a wiring diagram of the firing and safety circuits.

Figure 8 is a perspective detail view to an enlarged scale Zfllmi Patented Dec. 24*, 1957 Referring in detail to the drawings, 1 identifies a ring supported by the tank frame or body in any suitable manner, not shown, and supporting the tank turret, generally identified at 2, by antifriction bearing means 3. The armored top or cap 4 of the turret has an opening 5 within which the plate 6 is welded. The rocket launcher extends through the opening 7 in plate or cap 6 and is pivotaily mounted for elevation about a normally horizontal axis by a pair of aligned trunnions appearing upon Figures. 3, 4 and 6. Trunnion 8 and Q is also identified upon Figures 1 and 2 from which figures it will be noted that this trunnion is journaled in bearing block 10 bolted to the inner wall of top 4 adjacent opening 5. The other trunnion 9 is journaled in an identical manner on top 4 at the other side of opening 5, whereby the launcher may be elevated and depressed about the normally horizontal axis 11 defined by the trunnions. Standard or conventional elevating mechanism, not shown, such as is used to elevate the mm. gun on the Armys medium tanks, may be used to elevate the launcher about axis 11. Training of the launcher is effected by its pivotal movement as a unit with the turret about the normally vertical axis thereof.

The launching tube or crate, per se, is generally identitied by the numeral 12 and, referring to Figures 1, 2, 3 and 5, comprises a pair of armor side plates 13 and 14 connected at top and bottom by armor plates 15 and 16. The plates are rigidly connected, as by welding, to form a unitary frame or crate substantially square in interior cross-sectional dimensions, and extending from the interior of the turret to a point six inches or more ahead of the longest rocket to be fired. By this construction a rigid support is provided for the launcher tracks and the rockets are protected from the sides against premature detonation by enemy fire.

The top and bottom launching tracks 17 and 18 are duplicates in cross-sectional form and are secured to the top and bottom plates 15 and 16, respectively, as by bolts 19. From Figure 5 it will be noted that track 18 for example, comprises a central base portion 18a, having its side edges bent to form two spaced ribs or rails 13b and 180, and outer upturned flanges or terminal edge portions 18d and 18e. Corresponding portions of rail 17 are identified by like letters and it will be noted that the guide or rail portions of the two tracks define a circle of a diameter about equal to that of the head and tail portions of a rocket R to be launched. As shown upon Figure l, the tracks 17 and 18 extend forwardly a substantial distance ahead of the armor plates 13, M, 15 and 16 and are there rigidly united in fixed parallel relation, by vertical straps or braces 20 bolted to the flanges. By this construction, the rocket on ignition is positively guided along a straight launching path determined by the rotational position of the turret and the elevation of the launcher about trunnion axis 11.

A semi-cylindrical rotor 21 has an opening to receive the rear end of the launcher crate and is welded thereto as indicated at 22, Figure 2. The rotor has an axis coincident with trunnion axis 11 and a diameter slightly less than the distance from said axis to opening '7, whereby the opening is substantially closed for all angles of elevation of the launcher. A flange 23 is welded to and about the launcher tube just forwardly of rotor 21. A shield 24 of appropriate shape and size to obstruct and cover the small opening between the opening '7 in plate 6 and rotor 21, is bolted to flange 23 as by socket head screws 25. The aforesaid opening is closed by an obturating strip 26 of flexible material held in position by a ring 27 held to cap 7 by stud bolts 28.

As best shown in Figure 3, a breechblock housing 29 is welded over and across the rear end of the plates 13 to 16. This housing consists essentially of a fiat plate hav- 7 3;. ing its-vertical side edges shaped rearwardlyandthen'in wardly, to form vertically-disposed confronting guides or channels, as indicated at 29a. The housing has a generally square opening 30 symmetrically positioned with respect to the rear end of the launcher tube and"has.transverse dimensions a little less than those of the tube, whereby a rocket may freelypass' through the opening in loading. See also Figure 2.

A- breechblock 31, rectangular in outline, slidablyfits' the vertical guide channels and is movable vertically there'- between from a closed 'or upper position wherein it closes the aforesaid loading opening," to a secondoropen position wherein the loading opening is fully exposed forload-f' ing a rocket therethrough. The forward' fa'ce ofth'e.

breechblock 31 is formed witha circular recess 32 having a diameter materially larger than-the maximumtransverse dimension of opening 30-and sorelated,with,the'breech= block as to be in symmetrical position over the'rear of'the launcher tube when the breechblock is'in'upper'or'closed" "20 numeral 33, Figures 2, 3 and '7, aremounted 'with very" position. Obturatingrings, generally identifiedby "th'e small tolerances within recess SZ'and-areso -constructed in response to pressure within the launcher engendered by the firing of a rocket, to prevent theblow-back of-gases' between the housing 29 and' the'bree'chblock 31:

The breechblock is fully countcrweightedfor ease'of' vertical movement. This constructionincludes-apair*of undercut guide or trackmembers '34-and- 35bolted-to'the" respective left and right vertical 'sides' of housing 29. These members'are slidably engaged-by left and right' counterweight elements generallyidentifiedby-'the"nu merals 36 and 37. Left counterweight element-36 then,

is shaped in transverse horizontal cross-section-as=clearly shown upon Figure 3 to fit about'. guide rail 34'and be thereby limited to vertical translation.'= AforWa'rd"pro-' jectionor flange 36a forms asupport-for-a'box:38 posi= tioned. between the flange-and the launcher tubes This box is adapted to contain lead shot and is substantially.

coextensive in vertical dimensions, ;with"slide" 36; and'is bolted thereto by-bolts 39.

The rear flangeportion 36b'of counterweight--36-extends inwardly about housing 29 and has a vertical rack 42 secured to it and forming, ineffe'ct, an-inwardcon-' tinuation of the flange. A leadcounterweight 'bar,43 'is secured to flange 36b by bolts 44 to give added weight sufficient to counterbalance the weight ofbreechblock 31.. As the right counterweight 37 lSIaIl allochiral or mirror: duplicate of counterweight 36, itis-sutficienh-ireferrngparticularly to Figure3, to identify forward flange 37a,-

rear flange 37b, lead shot box40,1-bolts 41,2ri'ghtr'ack 45,

lead bar 46 and attaching bolts'47. The total-weight of i the counterweight parts just described. is isubstantially, equal to that ofbreechblock 31i, and the, parts zlflffixfid 1..

thereto.

A pair of vertically-disposed.-racks-48 and 49, Figures 3, 4 and 6, of the same length and tooth pitch as racks-42i an d are secured to breechblock; 31 adjacent andparallel with racks 42 and 45, respectively, as;-bycap screws 50.

A first pinion 51 is journaledpn'the, rearface of breech housing 29 and meshes with both ofqracks 42 :and 48.-

Likewise,,a second pinion 52 is journaled. at'therighton housing 29 and meshes with both ofracks 45' and 49. Bythis construction the breechblockiand counterweights are." constrained to move equally .and oppositely. and --thebreechblock may be opened and closed with minimum effort.

A pair of leaf-type buffer springe53 and- 54 are secured to the top of the breechblock housing -29. with their free ends extending downwardly to contact and engage .th e-- top of the breechblock as itrises into closed .POSlt-lOllf',

Stop'blocks 55 and 56, Figure .4, v re fixed tothe-lower.

ends of the housing 29 by stud boltsf57. Buffer, springs...

58 and 59,-Figures l and -2 are alsosecured by one of the bolts 57 to the housing in forwardly-extendingpositioned: that their free ends engage the lower surface ofv the respec-...

tive shot-box counterweights 38 and 40 when the breech- 4 blo'ckis raised tdclos'ed'pbsition'; For alikepurpos'e, springs 60' and 61', Figures 1 and 2, are fixed in forwardly-extending position to the top of housing 29 so that their free ends engage the top of boxes 38 and 40 as the counterweight assemblyrises in response to lowering of the breechblock. The springs just described serve to slow down the finalor limiting movements of the breechblockand its counterweights, and prevent excessive shock:

51. Shield 61 is correspondingly positioned at the'right" side in fixed relation with bar 46. A cooperatingpair of shields 62 and 63 are secured to the respective racks 48 and '49 in coextensive relation therewith. These shields are also generally Z-shaped in cross-section and each has its outermost flange extending beneath and slightly underlapping the contiguous edges of the shields 60 and 61, respectively. These shields thus act to conceal the racks and pinions at 'all'positions and thus prevent injury to operating personnel during opening and closing of the' breechblock.

Manually releasable'rneans are provided to lock the breechblockin either of its two extremepositions of fully open and fully closed. Suchmeans comprises a pairof slides 'or locking bolts 64 and 65 carried by the breechblock and transversely slidable'in aligned channels or grooves therein." These'bolts areso' positioned that when 'tl'1e"breechblock is "closed as'shown at Figure 6, the slides may be moved outwardly in opposite directions,- to cause theirends to engage in notches 66 and 67 in the inwardly-directed flange 'portion'of breechblock housing29." A second 'pair of'notches 68 and 69, Figures 4 and 6, are provided at the lower ends of the aforesaid flange portions of the breechblock housing and are 'so located that slides 64-and 65 may engage therein when the breechblock is fully open.

Simultaneous operation of the locking bolts is effected by mechanism including a handle or rod 70 fixed tothe" breechblock and'projecting rearwardly therefrom. A

rocker arm or control lever 71 is substantially coextensive" with handle 70 in transverse dimension and -has arm's pivoted at 72 and 73, Figure 3, to the handle. The rocker arm as a bar 71a integral with and connecting the forward ends of its arms. This bar has a longitudinal vslot 74, Figures 6 and 8, in its central portion.

A pair of bellcranks 75 and 76 are pivoted at 77 and 78, respectively, to a base plate 79 secured to the breechblock 31.

one arm of bellcrank 76. The remaining arms of the bellcrank have pins 82 which project rearwardly into slot 74 with a sliding fit therein. Thus, when handle 70"and rocker arm 71 are simultaneouslygrasped and pressed together, the resulting pivotal movement of the rocker" arm pivots bellcranks 75and 76 and withdraws 'bolts' 64 and 65 from the notches 66, 67 or 68, 69, as the case may be, whereby the breechblock may then be moved vertically. Coil springs 83 and 84, Figure 3,- are positioned within axial bores in the respective bolts and react against contiguous portions of the breechblock,- to. urge the bolts outwardlyinto locking positions. As best shown upon Figure 2, a cover plate 85 is secured to plate 79 and extends over the breechblock to protect the parts" just described.

Means .areprovided 'to releasably engagethe tail fin shroud rings of the rocket as-it is loaded intothe launcher to thereby locate it witliiiithe launcher tube in the proper A link'80 connects bolt; 64 with one arm of bellcrank 75. Likewise alink 81' connects bolt 65 with longitudinal position so that it may be electrically fired.

and automatically released for forward propulsion by its motor. These means are best shown upon Figures 2, 3 and 9. In Figure 2 it will be noted that lower or bottom plate 16 is centrally cut away just rearwardly of the fiat rear face of rotor 21, to provide an opening 86 in the bottom of the breech portion of the tube. A plate 87 has a fore and aft dimension equal to the distance between the aforesaid face of rotor 21 and breechblock housing 29. This plate is bolted to a square frame comprising front and rear strips 88 and 89 welded, respectively, to the rear face of rotor 21 and the forward face of housing 29, and side pieces, one of which is identified at 90, Figure l, welded across the ends of the strips 88 and 89. The side pieces are of greater vertical dimension than the strips 88 and 89 and are welded at their forward and rear ends to the rotor 21 and housing 29, respectively. The side pieces are also welded along their top edges, to the side portions of plate 16 bounding the opening 86. Sealing or obturating strips 91 are secured to plate 87 and the frame comprising parts 88, 89, 90, etc., and interfit when the plate 87 is bolted in place, to prevent the escape of propelling gases into the turret when a rocket is fired. The construction just described thus forms a sealed chamber within which the latching mechanism, to be described, is mounted.

A support 92, Figures 2, 3 and 9 is generally U-shaped in cross-section and has horizontally and outwardly-extending flanges bolted to and supported from, the rear horizontal portions of lower launching rail 18. The support has transversely spaced upstanding lugs at its rear ward end, one of which is identified at 92a, and which have aligned bearing openings to support a rear stop 93 for pivotal movement on pin 94. The stop is generally of inverted U shape in transverse section, with vertical sides embracing the support 92 and provides a forwardly and upwardly inclined top surface which projects upward ly through a cut-out 96, Figure 3, in bottom rail 18 and which is cammed downwardly by the shroud rings of a rocket as the latter is slid into loaded position. A spring 95, Figures 2 and 3, acts to urge the stop into the limiting position shown, a position determined by the engagement of lugs upon the stop with the bottom of the support.

A forward elongated stop 97 is generally U-shaped in transverse section to fit between the sides of support 92. This stop is pivoted on a pin 98 fixed in the sides of the support. A coil spring 99 urges the stop into the maximum clockwise position shown upon Figure 2 wherein a portion of the stop or latch projects upwardly through an opening 100 in bottom rail 18 into position to engage the forward shroud ring S when the rocket is properly loaded. Due to the fact that the pivot axis of the forward stop is below the ring-engaging face thereof, a sufficient forward thrust on the rocket as when its propelling charge is ignited, will cam the stop downwardly and release the rocket for flight. For the purpose of providing a firing circuit through ring S to the ignition squib of the rocket motor, the rear face of the stop, that is, the metal plate 101 (see also Figure 7) which actually engages the forward shroud ring, is electrically insulated from the remainder of the stop. For a like reason, the portions of the rails 17 and 18 which otherwise would engage the forward shroud ring when the rocket is in firing position, are cut away as indicated at 102 and 103, Figures 2 and 3. From Figure 2 it will be noted that the confronting faces of the two steps 93 and 97 are spaced so that as a rocket is slid into the launcher, stop 93 is cammed downwardly by the shroud rings and then snaps into place behind the rear ring as the front face of the forward ring engages the insulated face of stop 97. The rocket is thus releasably held in firing position and instantly released when its propellant is ignited.

The firing circuit is shown at Figure 7 and incorporates safety and signal features which make it impossible to fire a rocket unless and until the breechblock is fully closed. As a preliminary it should be explained that the two shroud rings S and T which surround and are connected with the stabilizing fins of the rocket are separate and distinct and that the forward ring S is electrically insulated from the other parts of the rocket. A lead then extends from this forward ring to the interior of the rocket motor where it connects with the electric squib of the igniter for the propellant.

For the purpose or making electrical contact with shroud ring S, 1 provide the launcher with an electrical contact for engaging the ring when the rocket is properly loaded. This contact is generally identified by the numeral 104, Figures 3 and it). This consists of a member L-shaped in cross-section having its horizontal and rigidly secured by screws 105, Figure 3, to the bottom of rail 18 so that its vertical or upstanding part projects through opening 100. This upstanding part 1041) is tapered, as clearly shown upon Figure 7, and its upper sharpened edge is so positioned as to engage shroud ring S and make a good electrical contact therewith when the rocket is in proper launching position. A lead 106 in the form of an armored cable is connected at one end with contact 104 and extends to a firing switch 107 forming a component part of a switch box 108 located at a convenient position within the turret. A second lead 109 extends from the switch 107 to a second or breech-operated microswitch 110. A signal lamp 111 is connected in shunt across switch 107 to be lighted when the breechblock is closed and a rocket is loaded into the launcher. The shunt circuit including the lamp 111 does not convey suflicient current to initiate the squib of the igniter for the propellent charge. As shown upon Figures 4 and 6, switch is fixed to the top of breech housing 29. This switch is normally open and is so positioned on the top of the housing 29 that its contact plunger 110a is engaged by the top of the breechblock only on the final increment of movement of the block into closed position, to thereby close the switch. Lead 109 is grounded through a signal lamp 112 and, accordingly is lighted when the breechblock and safety switch 114 are closed. A lead 115 extends from switch 110 to one terminal of a removable safety plug 113 having its other terminal connected with safety switch 114. A lead 116 connects switch 114 with one terminal of battery 117 having its other terminal grounded. Thus, in an obvious manner, the firing circuit is completed in'response to the closure of firing switch 107 when, and only when, (l) a rocket is properly loaded, (2) the breechblock is fully closed, (3) safety plug 113 is in position and (4) safety switch 114 is closed.

Any suitable mechanism may be provided to indicate the angle of elevation or depression of the launcher tube axis. One suitable form is shown in Figure 1, and comprises a dial plate 118 having a scale graduated in degrees and concentric of the axis of a pointer 119 pivoted upon the plate. The plate is fixed to a bracket 120 carried by the top of the turret.

An operating connection between the launcher and indicator consists of lever 121 fixed to the right trunnion of the launcher, and a second lever 122 pivoted at 123 on the bracket 120. An adjustable link 124 interconnects levers 121 and 122 in a parallelogram arrangement which causes the two levers to pivot equally and in the same direction of rotation when the launcher is elevated or depressed. A short link 125 connects lever 122 with pointer 119 in a second parallelogram arrangement such that the angular movement of the pointer is substantially the same as that of the launcher over the range of movement of the latter.

The operation of the launcher will be clear from the foregoing description and may be summarized as follows, it being assumed that the breechblock is closed. The gunner grasps handle 70 and lever 71, presses them togetherntomvithdraw 'breechblock- :locking; bolts 64 =and 65;:andsthen exerts'ra tdo-wnward thrust iupon :therhandle. Due; oztthe'rscomtterweight" arrangement-iepreviously :de-: scribed; the breechblock man he moved::dow-nwardly; with:.. a minimumrof .i'etfort'. Whenrthet -:breech-block:'kis fu1ly; .'5 lowered? or; opened releasea of: lBVCl'C271" enables springsz; 83cand.;84ito:=moverbolts :64;-and 651l1'1t0lTlOtCi'T6SZ68 "and .1 69, to thereby lock the breechblock.zinwopennpositionr As :the sbreechbl'oclcr movesrdownward'ly r switch; c.1107 is openedm.

Ararocket; is sli'd nthrough' :the': iopeninglcfllh into-:the. launchers tubes.v Ase-the? aforward taringrS uengages .reari: latch 93;; the. lattert is cammed downwardly, Whenv said :2 ringncontacts 2 forwardrstopqor 'face:.-d01; latch 93'- snapsintorpositionbehind the ream-ring thus releasably lock:-: ing. ;the2rocket'-:in-.:properifiring :positiontandvcausing: 104 I totcmakeizelectricalrcontact withntringr -S.;: Thexhandle 70 and lever. :71 .are againizgrasped, :pressed: together; to 1111-". lock theatbreechlrlock;;and:raised :to: therebyficlosezrthe; 1. breechblock Asirthe latter-imoveslinto closedposition, switchill'll is..closed.:f

Therelevating. "mechanismiwoftzthe launcher-sand the. traversing mechanism .of. the. turret =may= now be: operated toselevatenand train thew-tube to tth'e'zdesired target after which-,'plug. 113. being inzplace switcha107: is closed-.xto complete 5 the. firing:,.:circuit' and ignitei: the; :propellent't ch'argeaof'therocket: Theforward thrust engenderedxby the. burning propellantxforcesr forward? stop downwardly and thuszreleases the rockettor'fiightp. Due to the fact that therbreechblock; when: ;clo"sed,= gfo'rmssa hermetical I. seal :of the rearend of. the: launchenithe'propellant: gases i are deflected forwardly along- :the: spaces-z between the rocket and plates':13.- -16.' The :..open construction :rof p. tracks 17. and lflwincre'ases. thetrareaafonescape of Tthe gases about the rocketvduring initialz movement. thereof along the. launehen:

Suitable -.elevatingcmeans,z not shown,;;areprovided-by which the launcherimay be' elevated-and depressed about itsntrunnioni-axis .11.. It is contemplated to-utilize the standard elevating mechanism of' the-75 rnrnnta'nk. gun which-the launcher replacesa. Anxequilibrator spring 126 is provided to assist in balancing: the rexcess: weightv of the breechbl-oclg. housing: and .ncounterweights; over. that portion-of the launcher'forwardlyof the; trunnionsz:

Havingnow fully disclosedrthe invention-whatl claim and desire to secure by LettersPatent is:.

1. .A rocket-launching tube comprising firsttand second elongated metallic rectangular pl ates,-'said plates being of a length slightly greater than a rocket to be. fired'from said tube, means connecting said plates in opposed spaced parallel fixed relation, and first and second tracks secured to. the confronting surfaces of said plates, respectively, said tracks extending theentire length.:of and beyond said plates. and. rigidly braced .at their forward portions thereof,- each saidtrack comprising an elongatedvflat base of sheet metal lv ne in a first plane parallel with its plate, each edge of said sheet being .bent inwardly; toward the. other-plate and. then reversely outwardly into said plane, thenagain inwardly.- in a second plane normalto-said first plane, .each .said reversely-bent portion forminga rail,- whereby a total of fourrrails are formed, and-means :se-. curing the base portion only of eachtrack to its plate in longitudinallyrextending position therealong, the radially innermost portions .of..said rails collectively defining -in-' atransverse section, a circle. of. the same diametenas-a rocket to be fired from said tube.

2. A rocket-launching tube comprising four metallic plates having their contiguous edges rigidly unitedto form a tube of uniform rectangular cross-.sectiomsaidrgplateand having its side edges bent inwardly, then re versely'. .outwardl.y intovsaid plane, thenv again inwardly into..a terminalhedge, portion in a second plane'normal to said-:firsttplane each.said reversely bent portion forming a rail, meanssecuringthe base portion only of each track to its .plat e whereby said rails are. parallel and collectively define..in..transverse section a circle of the same diameter...as.-that=.-.of.a rocket to-be launched,-.said railsbeing longer. than.,and- -extending the entire length of:and 'forwardly; from...said tubefiand strap means rigidly connecting .corresponding terminal;.portions .of the respective.

tracks externally ,OfrSflid .tube.

3.. In .a rocket, launcher, ,four,- elongated imperforatev. plates..unitedalong, contiguous. side edges, =to=form a launchen .tube. generally square. in cross. section; track means withinasaidluhe to guide a rocket therealong in axial translation, a .breechblock-.housing secured to and acrossthe rearcndaofr-said tube in gas-tight relation with said plates andhaving an opening through which a rocket may be loaded into said tube, said housing providing confronting verticaljguide channels at opposite sides of" said-tube, a generally rectangular breechblock slidable in and .alonggsaidschannels a .pair of counterweights,1. means.fixedtotsaidvhousing and. guiding each counter- 7 weight for translation parallel withsaid breechblock at respectively ,opposite side edges thereof, first and second racks"isecurednin.confronting relation,to said breechblock and one counterweight, respectively, third and fourth ..racks .-.secured..inn-confronting relation to said breechblock .and theiotlrer.counterweight, respectively, a

first. :pinion .journaled zoncsaidxhousing and meshing with said. first. and. second. racks,.. and a second pinion jour-. naledlionssaid .housing-nandrmeshin'g ;with said. thirdjand fourthlracksi's a oppositely disposedaplates each. said track having each longitudinal-:edge :turnedinwardly toward the other track,

then.reversely,}outwardly ,into said plane, then laterally in said plane and again inwardly to terminate in a flange in..a .secondrplanenormal to said first plane, each said track forming aipair, of parallel rails, :said rails collectively defining :a circle; of-substantially the same-diameter ;as

that ofaa rocket'atoabelaunched-from.said tube, said tracksrzbeing longer thansand extending forwardly from said tube, spaced linkstrrigidly 7 connecting corresponding- 'fianges ofldppositejtracks externally. and forwardly of said tube,..a breech housing 'secured .to the breech end of said tubewinagas-tight.relation therewith and-having an opening .-through,which... a rocket maybexaxially loaded into said :tube saidr; housing providing. vertical confronting channels at. respectively: opposite sidcs of said tube, a 1

breechblock zslidably guidedflfor translation in. and along said-channels; fromta first position-overandclosing said 1 opening ,to asecond position'iclearaof said opening, manually releasablemeans-carried:bysaid breechblock for locking the samezin eitherof said positions',.firsti and sec- 0nd. vertical, guides. .fixed to opposite sides. of said housing,;.respectively,,.a counterweightjrnounted for translation,only.i'on andralongcach respective-guide, first and.

second confronting parallel-racks secured to .said breechbldck is in first position:

5 In( a device fora-launching. a rocket;from-within-an plates continuously connected along continuous longitublockiandone said counterweight respectively, third and T fourth confronting parallel racks-secured to said breechblock. and the-.othenof said coun'terweights respectively, a ,first. pinion v .,journaled.on saidhousing and meshing with .said third-,andfourthYracks, and -.means effecting -a gas-tight: sealz between said :housing vand saidbreechblocktabout the (rear,- end ofsaid: tube :when. the .breech-;1

dinal edges to form a launcher tube rectangular in transverse section, said tube being of a length slightly greater than the overall length of a rocket to be fired therefrom, and a pair of duplicate tracks secured within and extending along said tube, each said track comprising a central base portion secured centrally to and along opposite ones of said plates, respectively, each said plate having inwardly-directed reversely-bent side edges forming inwardly-extending linear guide rails, said rails being rigidly braces at their forward portions thereof for receiving a rocket loaded into said tube with a smooth sliding fit and guiding the same therealong in longitudinal translation.

6. In a launcher for a rocket, four elongated metallic plates rigidly united along contiguous side edges to form a tube substantially rectangular in cross-section, said tube being of a length equal to, at least, the overall length of a rocket to be fired therefrom, and first and second tracks each secured to and along the confronting inner surfaces of respective ones of oppositely-disposed plates, each said track comprising a fiat base of sheet metal secured to and extending centrally and longitudinally along its plate and having its longitudinal side edges turned inwardly and thence outwardly in a reverse bend to form a pair of laterally spaced parallel rails extending longitudinally along said tube, the radially innermost portions of said rails lying on the circumference of a circle of substantially the same diameter as a rocket to be fired from said launcher.

References Cited in the file of this patent UNITED STATES PATENTS 785,644 Unge Mar. 21, 1905 1,356,858 Fitzpatrick Oct. 26, 1920 2,391,864 Chandler Jan. 1, 1946 2,430,636 Gould Nov. 11, 1947 2,458,476 Lauritsen et a1. Jan. 4, 1949 2,478,774 Meinel Aug. 9, 1949 2,566,390 Weber Sept. 4, 1951 FOREIGN PATENTS 25,326 Great Britain of 1894 495,227 Germany Apr. 5, 1930 511,284 Great Britain Aug. 16, 1939 573,302 Great Britain Nov. 15, 1945 612,997 Great Britain Nov. 19, 1948 632,599 Great Britain Nov. 28, 1949 974,679 France Oct. 4, 1950 

